WO2015017492A1 - Système inverseur de poussée à ensemble charnière à translation-rotation - Google Patents

Système inverseur de poussée à ensemble charnière à translation-rotation Download PDF

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Publication number
WO2015017492A1
WO2015017492A1 PCT/US2014/048779 US2014048779W WO2015017492A1 WO 2015017492 A1 WO2015017492 A1 WO 2015017492A1 US 2014048779 W US2014048779 W US 2014048779W WO 2015017492 A1 WO2015017492 A1 WO 2015017492A1
Authority
WO
WIPO (PCT)
Prior art keywords
transcowl
thrust reverser
reverser system
stowed
nacelle
Prior art date
Application number
PCT/US2014/048779
Other languages
English (en)
Inventor
Alan Roy Stuart
Original Assignee
General Electric Company
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Company filed Critical General Electric Company
Priority to CN201480043131.6A priority Critical patent/CN105452641B/zh
Priority to JP2016531847A priority patent/JP2016534276A/ja
Priority to CA2919124A priority patent/CA2919124A1/fr
Priority to US14/908,557 priority patent/US10247137B2/en
Priority to EP14750671.1A priority patent/EP3027876A1/fr
Publication of WO2015017492A1 publication Critical patent/WO2015017492A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/42—Movement of components with two degrees of freedom
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to high-bypass gas turbine engines, and more particularly to thrust reverser systems utilized in high-bypass turbofan engines to provide thrust reversal by diverting air from a fan bypass duct.
  • FIG. 1 schematically represents a high-bypass turbofan engine 10 of a type known in the art.
  • the engine 10 is schematically represented as including a nacelle 12 and a core engine (module) 14.
  • a fan assembly 16 located in front of the core engine 14 includes a spinner nose 20 projecting forwardly from an array of fan blades 18.
  • the core engine 14 is schematically represented as including a high-pressure compressor 22, a combustor 24, a high-pressure turbine 26 and a low-pressure turbine 28.
  • a large portion of the air that enters the fan assembly 16 is bypassed to the rear of the engine 10 to generate additional engine thrust.
  • the bypassed air passes through an annular-shaped bypass duct 30 between the nacelle 12 and an inner core cowl 36 that surrounds the core engine 14, and exits the duct 30 through a fan exit nozzle 32.
  • the nacelle 12 defines the radially outward boundary of the bypass duct 30, and the core cowl 36 defines the radially inward boundary of the bypass duct 30 as well as provides an aft core cowl transition surface to a primary exhaust nozzle 38 that extends aftward from the core engine 14.
  • the nacelle 12 is typically composed of three primary elements that define the external boundaries of the nacelle 12: an inlet assembly 12A, a fan cowl 12B interfacing with an engine fan case that surrounds the fan blades 18, and a thrust reverser system 12C located aft of the fan cowl 12B.
  • the thrust reverser system 12C comprises three primary components: a translating cowl (transcowl) 34A mounted to the nacelle 12, a cascade 34B mounted within the nacelle 12, and blocker doors 34C.
  • the lower and upper halves of FIG. 1 represent the thrust reverser system 12C stowed and deployed, respectively.
  • the cascade 34B is typically a fixed or translating structure of the nacelle 12, whereas the transcowl 34A can be seen in the upper half of FIG. 1 as having been translated aft to expose the cascade 34B and deploy the blocker doors 34C into the duct 30 using a link arm 34D.
  • Translation of the transcowl 34A can be provided with a slider track (not shown) oriented roughly parallel to the axis of the engine 10.
  • the blocker doors 34C are adapted to be pivotally deployed from their stowed position radially inward from the cascade 34B (lower half of FIG. 1) to their deployed position (upper half of FIG.
  • transcowls of the type represented in FIG. 1 are often configured to pivot radially outward from the engine to permit maintenance access to, for example, the core engine.
  • FIG. 2 schematically represents a cross-section of a portion of the transcowl 34A taken perpendicular to the axis of the engine 10.
  • the transcowl 34A is equipped with two or more hinges 40 (of which one is visible in FIG. 2) that are pivotably coupled to an edge of a hinge beam 42.
  • the opposite edge of the hinge beam 42 is slidably connected to a slider track 44, which is represented in FIG.
  • the hinge beam 42 enables the transcowl 34A to translate along the slider track 44 (into the plane of FIG. 2) between stowed and deployed (aft) positions of the transcowl 34A.
  • the hinges 40 are aligned on an axis roughly parallel to the slider track 44, and pivotably connect the transcowl 34A to the hinge beam 42 to enable the transcowl 34A to rotate from its stowed position to an open position that permits maintenance access. While such an arrangement serves its intended purpose, thrust reverser systems that are capable of reducing weight, distributing load in and improved manner, and promoting compactness are desirable.
  • the present invention provides a thrust reverser system suitable for high-bypass turbofan engines of types used in aircraft.
  • the thrust reverser system is particularly adapted for use in a gas turbine engine having a nacelle surrounding a bypass duct.
  • the thrust reverser system includes a transcowl having a stowed position, a deployed position, and an open position.
  • the transcowl is adapted to translate from the stowed position to the deployed position in an aft direction of the gas turbine engine to define a circumferential opening within the nacelle.
  • a hinge assembly couples the transcowl to a fixed structure that does not translate when the transcowl is translated in the aft direction.
  • the hinge assembly includes first and second members coupled to each other. The first member is connected to the transcowl for translation therewith in the aft direction of the gas turbine engine, and the second member is connected to the fixed structure.
  • the second member defines a channel in which a portion of the first member is slidably received.
  • the first and second members are configured to enable the portion of the first member to translate within the channel in the aft direction of the gas turbine engine corresponding to a translational movement of the transcowl relative to the nacelle between the stowed and deployed positions of the transcowl.
  • the first and second members are further configured to enable the portion of the first member to rotate within the channel corresponding to a pivotal movement of the transcowl relative to the nacelle between the stowed and open positions of the transcowl.
  • a thrust reverser system is installed on a gas turbine engine that has a core engine, a core cowl surrounding the core engine, a nacelle surrounding the core cowl and comprising a fan cowl, and a bypass duct defined by and between the nacelle and the core cowl.
  • the thrust reverser system includes a transcowl translationally and rotationally mounted to the nacelle.
  • the transcowl has a stowed position, a deployed position, and an open position.
  • the transcowl is adapted to translate from the stowed position to the deployed position in an aft direction of the gas turbine engine and away from the fan cowl to define a circumferential opening therebetween.
  • the thrust reverser system further includes a cascade exposed to the bypass duct when the transcowl is in the deployed position.
  • a hinge assembly couples the transcowl to a fixed structure that does not translate when the transcowl is translated in the aft direction.
  • the hinge assembly includes a hook member connected to the transcowl and a slider track connected to the fixed structure so as not to translate when the transcowl is translated in the aft direction.
  • the slider track defines a slider channel in which a hook portion of the hook member is slidably received.
  • the hook member and the slider track are configured to enable the hook portion to translate within the slider channel in the aft direction corresponding to a translational movement of the transcowl relative to the nacelle between the stowed and deployed positions of the transcowl.
  • the hook member and the slider track are further configured to enable the hook portion to rotate within the slider channel corresponding to a pivotal movement of the transcowl relative to the nacelle between the stowed and open positions of the transcowl.
  • a technical effect of the invention is the ability to provide two different motions of a transcowl, namely, translational and pivotal, through the use of a hinge assembly that enables both deployment of a thrust reverser system and maintenance access to other components of a gas turbine engine in which the thrust reverser system is installed.
  • Preferred aspects of such an arrangement include the ability to reduce the weight and space occupied by a thrust reverser system and its components.
  • FIG. 1 schematically represents an axial (side) sectional view of a high-bypass turbofan engine, and schematically represents a thrust reverser system in stowed and fully deployed positions in the lower and upper halves of the view, respectively.
  • FIG. 2 schematically represents a cross-sectional view of a portion of a transcowl that is adapted for translational and rotational movement in accordance with a known configuration in the prior art.
  • FIG. 3 schematically represents a cross-sectional view of a portion of a transcowl that is adapted for translational and rotational movement in accordance with a nonlimiting embodiment of the present invention.
  • FIG. 4 schematically represents a detail showing a hinge assembly that provides a combined translational and rotational connection for the transcowl of FIG. 3.
  • FIGS. 3 and 4 schematically represent cross-sectional views of a portion of a transcowl (translating cowl) taken approximately perpendicular to the axis of a high-bypass gas turbine (turbofan) engine in accordance with a nonlimiting embodiment of the invention.
  • a transcowl translating cowl
  • Turbofan gas turbine
  • the transcowl 34A of FIGS. 3 and 4 is desired to have both a translational and rotational movement capability. Specifically, in addition to being capable of translating aft to deploy the thrust reverser system 12C, the transcowl 34A of FIGS. 3 and 4 is also configured to pivot radially outward from the nacelle 12 to permit maintenance access to, for example, the core engine 14.
  • the transcowl 34A is represented in FIGS. 3 and 4 as equipped with a hinge assembly 50 adapted to provide means by which the transcowl 34A is able to translate and pivot relative to the nacelle 12 and an engine pylon 13.
  • the hinge assembly 50 includes at least two members, first member 52 also referred to as a hook member and second member 58 also referred to as a slider track (FIG. 4) that are coupled together in a manner that enables a portion 56 of a first member52 of the members 52 and 58 to translate within a portion 60 of a second member 58 of the members 52 and 58 in the aft direction of the engine 10, corresponding to a translational movement of the transcowl 34A relative to the nacelle 12 between stowed and deployed positions of the transcowl 34A.
  • first member 52 also referred to as a hook member and second member 58 also referred to as a slider track (FIG. 4) that are coupled together in a manner that enables a portion 56 of a first member52 of the members 52 and 58 to translate within a portion 60 of a second member 58 of the members 52 and 58 in the aft direction of the engine 10, corresponding to a translational movement of the transcowl 34A relative to
  • the members 52 and 58 are coupled together to enable the portion 56 of the first member 52 to rotate within the portion 60 of the second member 58, corresponding to a pivotal movement of the transcowl 34A relative to the nacelle 12 between the stowed and open positions of the transcowl 34A.
  • first and second members 52 and 58 will be referred to as a hook member 52 and a slider track 58, respectively, with the former having a hook 56 slidably disposed in a slider channel 60 defined by and within the latter for translational and rotational movement therein.
  • the hook member 52 is connected to or otherwise extends from an edge 54 of the transcowl 34A, whereas the slider track 58 is a fixed structure, for example, connected to the pylon 13 (FIG. 3), such that the slider track 58 does not translate or rotate during deployment of the thrust reverser system 12C. Sliding of the hook 56 within the slider channel 60 in directions into and out of the plane of FIGS.
  • transcowl 34A to translate between a stowed position and a deployed position, the latter exposing the cascades 34B to provide a thrust reversal effect as previously described with reference to FIG. 1.
  • rotation of the hook member 52 within the slider channel 60 enables the transcowl 34A to pivot in the plane of FIGS. 3 and 4, corresponding to a rotational movement between the stowed position and what will be termed herein an open position of the transcowl 34A that permits maintenance access to other components of the engine 10, for example, the core engine 14.
  • the hook member 52 is further configured to define a bearing wall 62 that slidably bears against an outer surface of the slider track 58 when the transcowl 34A is in its stowed and deployed positions and, as represented in FIG. 4, may slide free of the slider track 58 as the transcowl 34A is pivoted from its stowed position to its open position, as seen in FIG. 4.
  • a bearing wall 62 that slidably bears against an outer surface of the slider track 58 when the transcowl 34A is in its stowed and deployed positions and, as represented in FIG. 4, may slide free of the slider track 58 as the transcowl 34A is pivoted from its stowed position to its open position, as seen in FIG. 4.
  • the hook 56 and bearing wall 62 cooperate to limit circumferential movement of the transcowl 34A relative to the pylon 13 while the transcowl 34A is in its stowed position, yet provides a translational connection to the slider track 58 to enable the transcowl 34A to translate along the slider track 58 (into and out of the planes of FIGS. 3 and 4).
  • the channel 60 is preferably linear and roughly parallel to the axis of the engine 10, in which case the hook 56 would be axially aligned within the channel 60 with hooks (not shown) of any other hook members associated with the transcowl 34A.
  • the hinge assembly 50 as including attach bolts 66 (or other means) adapted to attach the assembly 50 to the pylon 13 (or some other suitable fixed structure). Alternatively, the hinge assembly 50 could be built into the pylon 13 or other suitable fixed structure (not shown).
  • the slider track 58 is configured to define an abutment wall 64 that is contacted by a distal end 68 of the hook 56 to establish a limit to which the hook 56 is able to rotate within the slider channel 60.
  • the hook 56 and abutment wall 64 cooperate to limit the extent to which the transcowl 34A can be pivoted relative to the cowl 12 as the transcowl 34A is pivoted from its stowed position to its open position.
  • FIG. 4 further represents the slider track 58 as defining an arcuate depression 70 contacted by an outer surface of the hook 56, thereby assisting to stabilize the hook 56 within the slider channel 60 during pivotal movement of the transcowl 34A
  • the slider track 58 is represented in FIGS. 3 and 4 as comprising a flange 72 to which the bolts 66 (or similar mounting means) are fastened, and as further comprising a bridge 74 that can be seen in FIG. 4 as interconnecting portions of the track 58 that define the abutment wall 64 and flange 72.
  • the hook member 52 can also be seen in FIG. 4 as having a bridge 76 that interconnects portions of the hook member 52 that define the hook 56 and bearing wall 62.
  • the bridge 76 of the hook member 52 is represented as defining a clearance with the abutment wall 64 to avoid engagement with the abutment wall 64 when the transcowl 34A is in its stowed and/or deployed positions, thereby avoiding moment transfer and higher stress at the joint.
  • distal end 68 of hook 56 is represented as defining a clearance with the abutment wall 64 to avoid engagement with the abutment wall 64 when the transcowl 34A is in its open position, thereby also avoiding moment transfer and higher stress at the joint.
  • This clearance also allows flexibility for build tolerance and/or alignment of the components.
  • the weight of the thrust reverser system 12C may be minimized and/or the overall compactness of the system 12C promoted as a result of the hinge assembly 50 being adapted to provide both a translational and pivotal motion capability to the transcowl 34A.
  • the thrust reverser system 12C lacks any intermediate component located between and coupling the fixed slider track 58 and the pivotable and translatable hook member 52. From the above discussion and depictions in FIGS. 3 and 4, it should be appreciated that the translational-rotational motion of the transcowl 34A is not dependent on any particular type of thrust reverser design, aside from the requirement that the system is capable of turning the air flow within the bypass duct 30 to generate a thrust-reversing effect.
  • the thrust reverser system 12C and its individual components can be constructed of various materials, including metallic, plastic and composite materials commonly used in aerospace applications and fabricated by machining, casting, molding, lamination, etc., and combinations thereof. Some examples of materials that could be utilitzed for constructing the thrust reverser system 12C and/or its individual components include aluminum, titanium, steel or graphite epoxy composite, as well as other materials with similar properties.
  • hinge assembly 50 may include a single continuous hook member 52 associated with a single continuous slider track 58. Alternatively, hinge assembly 50 may be comprised of one or more hook members 52 associated with one or more slider tracks 58.
  • a single continue hook member 52 associated with a single continuous slider track 58 acts to continuously distribute the load along the length of hinge assembly 50. Additionally, surfaces of hook member 52 that come into contact with surfaces of slider track 58 or surfaces of slider track 58 that come into contact with surfaces of hook member 52 may have a nylon lining or use of another suitable material to prevent wear.

Abstract

L'invention concerne un système inverseur de poussée (12C) approprié à un turboréacteur à taux de dilution élevé (10) de type à nacelle (12). Le système inverseur de poussée (12C) comprend un manchon coulissant (34A) comportant des positions rangée, déployée et ouverte. Un ensemble charnière (50) raccorde par translation et rotation le manchon coulissant (34) à une structure fixe (13) qui n'effectue pas de translation lorsque le manchon coulissant (34) est translaté dans la direction arrière. L'ensemble charnière (50) comprend un premier élément (52) raccordé au manchon coulissant (34) pour effectuer avec celui-ci une translation, et un second élément fixe (58) qui forme un canal (60) dans lequel est reçue coulissante une partie du premier élément (52). Les premier (52) et second (58) éléments sont conçus pour permettre la translation de la partie du premier élément (52) à l'intérieur du canal à coulissement (60) dans une direction arrière correspondant à un mouvement de translation du manchon coulissant (34), et pour permettre la rotation de la partie du premier élément (52) à l'intérieur du canal (60) correspondant à un mouvement pivotant du manchon coulissant (34).
PCT/US2014/048779 2013-07-30 2014-07-30 Système inverseur de poussée à ensemble charnière à translation-rotation WO2015017492A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
CN201480043131.6A CN105452641B (zh) 2013-07-30 2014-07-30 具有平移‑旋转铰接组件的推力反向器系统
JP2016531847A JP2016534276A (ja) 2013-07-30 2014-07-30 並進及び回転式ヒンジ組立体を備えた逆推力システム
CA2919124A CA2919124A1 (fr) 2013-07-30 2014-07-30 Systeme inverseur de poussee a ensemble charniere a translation-rotation
US14/908,557 US10247137B2 (en) 2013-07-30 2014-07-30 Thrust reverser system with translating-rotating hinge assembly
EP14750671.1A EP3027876A1 (fr) 2013-07-30 2014-07-30 Système inverseur de poussée à ensemble charnière à translation-rotation

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361859806P 2013-07-30 2013-07-30
US61/859,806 2013-07-30

Publications (1)

Publication Number Publication Date
WO2015017492A1 true WO2015017492A1 (fr) 2015-02-05

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2014/048779 WO2015017492A1 (fr) 2013-07-30 2014-07-30 Système inverseur de poussée à ensemble charnière à translation-rotation

Country Status (6)

Country Link
US (1) US10247137B2 (fr)
EP (1) EP3027876A1 (fr)
JP (1) JP2016534276A (fr)
CN (1) CN105452641B (fr)
CA (1) CA2919124A1 (fr)
WO (1) WO2015017492A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9771161B2 (en) 2015-07-16 2017-09-26 Rohr, Inc Beam with hybrid cross-sectional structure
US9845769B2 (en) 2015-05-05 2017-12-19 Rohr, Inc. Plastic core blocker door

Families Citing this family (6)

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Publication number Priority date Publication date Assignee Title
GB2564891A (en) * 2017-07-26 2019-01-30 Short Brothers Plc Nacelle with thrust reverser
US10907577B2 (en) * 2017-10-23 2021-02-02 Rohr, Inc. Translating lock for pivot door thrust reverser
FR3079878A1 (fr) * 2018-04-05 2019-10-11 Airbus Operations Turboreacteur comportant une nacelle equipee d'un systeme inverseur comportant un capot articule
FR3085726B1 (fr) * 2018-09-07 2020-12-11 Safran Nacelles Inverseur de poussee a structure mobile en c pour ensemble propulsif d’aeronef, et procede de maintenance s’y rapportant
FR3092145A1 (fr) * 2019-01-24 2020-07-31 Airbus Operations Turboreacteur double flux comportant une serie de lames rotatives pour obturer la veine du flux secondaire
US11731774B2 (en) 2020-01-06 2023-08-22 Rohr, Inc. Dual axis hinge radial displacement limiter

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Publication number Priority date Publication date Assignee Title
EP0109219A2 (fr) * 1982-11-12 1984-05-23 LUCAS INDUSTRIES public limited company Dispositif d'inversion de jet pour un moteur à turbine à gaz
US5806302A (en) * 1996-09-24 1998-09-15 Rohr, Inc. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser
FR2980173A1 (fr) * 2011-09-16 2013-03-22 Aircelle Sa Ensemble arriere de nacelle pour turboreacteur

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FR2903454B1 (fr) 2006-07-05 2008-08-29 Airbus France Sas Nacelle de reacteur d'aeronef et aeronef comprenant une telle nacelle
FR2907170B1 (fr) 2006-10-11 2008-12-12 Aircelle Sa Inverseur de poussee a grilles pour moteur a reaction
FR2908109B1 (fr) * 2006-11-03 2008-12-12 Aircelle Sa Element de nacelle de turboreacteur

Patent Citations (3)

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Publication number Priority date Publication date Assignee Title
EP0109219A2 (fr) * 1982-11-12 1984-05-23 LUCAS INDUSTRIES public limited company Dispositif d'inversion de jet pour un moteur à turbine à gaz
US5806302A (en) * 1996-09-24 1998-09-15 Rohr, Inc. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser
FR2980173A1 (fr) * 2011-09-16 2013-03-22 Aircelle Sa Ensemble arriere de nacelle pour turboreacteur

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9845769B2 (en) 2015-05-05 2017-12-19 Rohr, Inc. Plastic core blocker door
US9771161B2 (en) 2015-07-16 2017-09-26 Rohr, Inc Beam with hybrid cross-sectional structure

Also Published As

Publication number Publication date
US20160169156A1 (en) 2016-06-16
CA2919124A1 (fr) 2015-02-05
CN105452641A (zh) 2016-03-30
US10247137B2 (en) 2019-04-02
CN105452641B (zh) 2017-07-18
EP3027876A1 (fr) 2016-06-08
JP2016534276A (ja) 2016-11-04

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